Jet reaction and return flow propulsion means



April 5, 1960 G. s. MITTELSTAEDT 2,931,170

JET REACTION AND RETURN 11.0w PROPULSION MEANS Filed June 27, 1956 I 2 3A i C B I I I I l l l l I I I I I I l I I I l l l l l I I llllll4 V F G3 INVENTOR JET REACTION AND RETURN FLOW PROPULSION MEANS Georg S.Mittelstaedt, Brooklyn, Application June 27, 1956, Serial No. 594,160 17Claims. (Cl. 6035.6)

V This invention-:relates to engines, including reaction engines,and-including jet and turbojet systems. be used as a propulsion meansfor aircraft, marine vessels, vehicles, or other movable objects. Italso relates to. propulsion in part by reaction of a jet.

The invention relates particularly to the return or reverse flow, whichI discovered to be associated with an annularly' discharged fluid streamcooperating with a centerplate, which may have any shape, character orform. In the text and claims: By return flow or reverse flow is. alsomeant forward flow and centripetal flow; By fannular is alsomeant anyencircling outline orfigure. 1By centerplate is also meant any centralbody, central portion, or any central covering or dividing means. Y

An object of this invention is to improve reaction engines.

Another object of this invention is to create a simple and practicable.form of auxiliary propulsion means in cooperation with the annularlydischarged exhaust stream of a jet reaction device. I i

. Another object is to gain motion by utilizing the above mentionedreturn flow'efi'ct.

Another object is to utilize said return flow efiect to drivea turbineor other device.

7 Still another object is to provide cooling and ease and simplicity ofinstallatioh V These and other objects will become apparent in thedescription below, in which characters of reference refer to like-namedparts in the drawing.

The drawing shows sectional views of various devices, illustrating theapplication of the invention, but the invention is not limited to theparticular devices illustrated.

Figure 1 shows a rocket type reaction engine, illustrating theapplication of the invention.

Figure 2 shows a turbojet type reaction engine with an inner turbine anda return-flow operated outer turbine, illustrating the application ofthe invention.

Figure 3 shows a turbojet type reaction engine having a return-flowoperated turbine, illustrating the application of the invention.

Referring in detail to the drawing, Figure 1 shows a rocket typereaction engine, where the numeral 1 indicates the case and 2 thepropellant. The numeral 3 indicates an annular exhaust nozzle, 4 acenterplate, 6 shows a return-flow actuated body, and 5 shows aconnecting member between centerplate 4 and body6. The arrows indicatethe character and approximate directions of the flow. A indicates theannular flow, B the converged or full flow, and C indicates the returnflow which I utilize in this invention to gain motion.

Figure 2 shows a turbojet type reaction engine, where the numeral 1indicates the case, 7 the compressor, 8 the combustion chamber or flametubes, and 9 the inner turbine. nozzle, 4 a centerplate and 10 areturn-flow operated turbine, shown mounted on the same shaft 11 withthe compressor 7. The arrows indicate the character and The numeral 3indicates the annular exhaust,

nited States Patent It may ICC .5" 2 I approximate directions of theflow. A indicates the annular flow, B the converged or full flow, and Cindicates the return flow which I utilize in this invention to gainmotion.

Figure 3 shows a.-turbojet type reaction engine, where the numeral 1indicates the case, 7 the compressor, 8 the combustionchamber. or flametubes, 3 indicates the annular exhaust nozzle, 4 a centerplate, and 10 areturn-flow operated turbine, shown mounted onthe sameshaft 11 withcompressor 7. "The arrows indicate the character and approximatedirections of the-flow. A indicates the annular flow, B the converged orfull flow, and C indicates the return flow which I utilize in thisinvention to gain motion.

The annular flow A converges to a full flow B; and in association withcenterplate 4 a return flow. C is created. I have conducted numerousexperiments and I have found that theabove defined reverse flow Cdevelops essentially as illustrated and described. I believe that theconverging annular fluid stream creates a near vacuum or low pressurepocket at C, andan exterior medium, such as part of the fluid stream isforced into said pocket, thereby creating the reverse flow C.

I propose-to utilize the described reverse flow C to impinge on atargetsuriace or body 6, which may have any suitable shape, character orform. Said bodyf6 is situated rearward of the centerplate4 andiiwithinthe return flow region C, said body 6 being preferably smaller in'diameter .thansaidcenterplate 4. -..,It is evident that the body 6 islocated away from the fluid stream. portions-A-and B. It is also evidentthat;said body 6 is located'inthe path of the described reverse flow C,said reverseflow C impinging on said body 6, thereby creating motiom:The target surface for said return flow C may be part of thecenterplate or engine structure, and said centerplate may be part of theengine structure."

the turbine 10 which is located rearward, of the center-' Such abody-6may bevaned and have the characteristics of'a;turbine, and the inventionembraces the use of a turbine or related device in cooperation with thedefined reversefiow C. A In this'application of the invention thedescribed return flow C is used to furnish power to operate plate 4 andwithin the return flow region C, said turbine 10 being preferablysmaller in diameter than said centerplate 4. The turbine 10 may drive acompressor 7 for furnishing an airstream or other form of compressedair, which may be used in the engine. It is evident that the turbine 10is located away from the fluid stream portions A and B. It is alsoevident that said turbine 10 is located in the path of the describedreverse flow C, said reverse flow C impinging on said turbine 10,thereby creating rotation and motion.

The described turbine may be attached to any suitable part of thestructure. The turbine 10 may be coaxial with the compressor 7, and maybe mounted on the same shaft 11 with the compressor 7.

It is part of this invention to utilize this described reverse flow tosecure a cooling eflect on the turbine or in the propulsion system.

It is to be noted that changes in form and construction may be madewithout departing from the spirit or scope of the invention.

I claim:

1. A jet reaction and return flow propulsion device, including acombustion chamber, an annular nozzle for leading the exhaust from saidcombustion chamber to atmosphere, and a centerplate encircled by saidannular nozzle, said nozzle discharging an annular fluid stream, saidannular fluid stream converging to a full stream and creating a returnflow in cooperation with said centerplate, the return flow region lyingwithin the confines of the annular and converging portion of said fluidstream 4..A system according to claim 2, an inner turbine locatedupstream of the terminal of the exhaust nozzle, said return-flow turbinebeing connected with said inner turbine.

5. A system according to claim 4, said return-flow turbine having thesame shaft with said inner turbine and with said. compressor.

.6. A jetreaction and return flow propulsion device, including acombustion chamber, an annular nozzle, and a centerpiece encircled bysaid annular nozzle, said nozzle leading the exhaust from saidcombustion chamber to atmosphere; said nozzle discharging an annularfluid stream, said annular'fiuid stream converging and creating a returnflow in cooperation with said centerpiece, a turbine situated rearwardof said centerpiece and in the path of said return flow, said returnfiow exerting a pressure on said turbine, thereby creating motion androtation.

7. A system accordingto claim 6, a compressor for furnishing anairstream for use in the combustion chamber, said return-flow turbinebeing connected with said compressor.-

8. Ajsystem according to claim 7, said return-flow turbine having the:same shaft with said compressor.

9. .A system according to claim 7, an inner turbine located between thenozzle terminal and the combustion chamber, said return-flow turbinebeing connected with said inner turbine 10.. A'system according to claim9, said return-flow turbine having the same shaft with said innerturbine and with said compressor.

- 1'1. In a device of the-class; described, a combustion chamber, an.annular nozzle,- and a central part encircled by'said annular nozzle,said nozzle leading the exhaust from said combustion chamber toatmosphere, said nozzle discharging an annular exhaust stream, saidannular exhaust stream expanding inward to a full stream and creating areturn fiow in cooperation with said central part, a means to utilizesaid return flow to gain motion, said means comprising a target situatedin the path of said return flow, said return flow exerting pressure onsaid target, tending to move said target.

12. A system according to claim 11, said target comprising a bodysituated in the path of said return flow, said return flow exertingpressure on said body, tending to move said body forward.

13. A system according to claim 11, said target com prising a bodyrearward of said central part and separated with a space therefrom, asupport for said body, said body being smaller in diameter than saidcentral part.

14. A system according to claim 11, said target comprising a turbinesituated in the path of said return flow, said return flow impinging onsaid turbine, thereby creating rotation.

' 15. A system according to claim 11, said central part having a fiatend-surface parallel with the nozzle opening.

16. A propulsion device, including a means to produce a fiow, an annularnozzle to discharge said flow annularly, a centerplate encircled by saidannular nozzle, and a body rearward of said centerplate and separatedwith a space therefrom, a support for said body, said body being smallerin diameter than said centerplate, the annular flow expanding inwardafter discharge from said annular nozzle and creating a return flow incooperation with said centerplate, said return flow exerting pressure onsaid body, tending to move said body.

17. A system according to claim 16, said body being vaned and rotatablymounted.

References Cited in the file of this patent UNITED STATES PATENTS2,256,198 Hahn Sept. 16, 1941 2,489,953 Burney Nov. 29, 1949 2,601,311McCormick June 24, 1952 OTHER REFERENCES The Rocket Combustion Motor byDr. Sanger, printed in Astronauticsfor October 1936, pages 4 and 5.Principles of Aerodynamics (Dwinnell), published by McGraw-Hill', 1949,page 166.

